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The Environmental Control and Life Support System (ECLSS) for both MPLM and APM is developed by Dornier. One of the main ECLSS functions to be realized is the atmosphere pressure control of the module. It includes the Cabin Depressurisation, the Positive Pressure Relief, and the Negative Pressure Relief. In order to verify the functionality of the atmosphere pressure control system (ACS) analyses of different scenarios have to be performed. The analysis method including the governing equations of the three ACS functions is described. The analyses are performed with a Dornier developed software program that solves the set of equations numerically. The results of the analyses in terms of pressure and temperature transients are presented and discussed with respect to the boundary conditions and the influence of humidity.

The Mini Pressurized Logistic Module (MPLM) of the International Space Station (ISSA) is foreseen for the transport of service equipment, experiment racks and service racks to the station. For the orbital operational phase it needs an Environmental Control and Life Support System (ECLSS) to make it commissionable for the astronauts. Because of its short mission time and the usage as a transport vehicle it has no completely autonomous ECLSS functionality. The Temperature and Humidity Control (THC) is supported by the Space Station via an Inter Module Ventilation Interface (IMV l/F). The MPLM ECLS has the requirement to suck revitalized air through the IMV l/F and mix it up with the recirculated air in order to provide a comfortable atmosphere in the MPLM habitable area. The fulfillment of the hydraulic and thermal requirements is verified by test and analysis. With this paper we provide the hydraulic analysis performed with ECOSIM, an ESA approved software tool.

The Mini Pressurized Logistics Module (MPLM) is being developed as the Italian contribution to the International Space Station (ISS) Programme. To improve the efficiency of European space programmes, the Italian Space Agency (ASI) and the European Space Agency (ESA) have decided to increase the commonality between the MPLM and the Columbus Orbital Facility (COF), the European laboratory contribution to the ISS. As a result ASI will provide to ESA a primary structure of the MPLM to be used as the primary structure for COF; in return ESA will provide to ASI the ECLS subsystem for the MPLM, which is a subset of the COF ECLS subsystem. This paper describes the functions of the MPLM ECLS subsystem, the analytical and developmental activities performed by the ECLS Contractor, Daimler-Benz Aerospace Dornier GmbH, and the development status of the various ECLS equipment.

The thermal behaviour of spacecraft especially of manned ones is governed by various thermophysical effects. Heat transfer by radiation, conduction and convection influence the overall behaviour of the spacecraft. Energy production, distribution and consumption have also strong impacts on the temperature field prevailing in the spaceplane. Moreover, chemical reactions, metabolic rates of the crew and external heat loads determine the thermal behaviour of the spacecraft. For design and optimisation of the system and its subsystems a mathematical model is required which describes these effects. There are many tools available with which parts of the above mentioned aspects can be covered. However, a comprehensive model of a spacecraft reflecting all aspects can only be established with a combination of different simulation tools. In the present paper methods are described, how different simulation tools can be used to set up such a model.